固冲发动机双下侧二元进气道设计研究  

A Code for Designing 2-D Mixed-Compression Inlet of Solid Propellant Ramrocket

作　　者：鲍福廷[1] 李进贤[1] 赵飞[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《西北工业大学学报》2002年第4期590-593,共4页Journal of Northwestern Polytechnical University

摘　　要：结合整体式固体火箭冲压发动机的特点 ,探讨了双下侧二元进气道的设计方法。文中对进气道的结构、型面设计方法和性能估算进行了较为详细地研究。通过编程实现了设计的程序化 ,并通过算例对一假想的固冲发动机进行了优化设计与计算。We were under contract to develop a code for designing 2-D mixed-compression inlet of SPR(Solid Propellant Ramrocket). The contract required us to so design the inlet configurations as to get high pressure recovery ratio. Subsection 1.1 explains four general considerations we considered necessary in our development work. Subsection 1.2 discusses four configuration considerations: (1) supersonic pressure expansion section(subsubsection 1.2.1), (2) throat section (subsubsection 1.2.2), (3) subsonic pressure expansion section(subsubsection 1.2.3), and (4) form of inlet exit(subsubsection 1.2.4). Our code uses eqs.(2) through (5) to evaluate the performance of our 2-D mixed-compression SPR inlet; in particular, it computes pressure recovery ratio and mass flow coefficient. Finally, section 3 presents a numerical example to demonstrate the code capability.

关 键 词：双下侧二元进气道 固体火箭冲压发动机 优化设计 计算 航空发动机 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程] V235